An analysis of inviscid transonic flows over three-dimensional wings using the discontinuous galerkin solver in su2

In simulating flows over aeronautical objects, engineers cope with balancing between two goals: accuracy and computational feasibility. Because of the modest accuracy and the computational cost, conventional second-order accurate numerical methods have been successful in aiding engineers to analyze fluid flows. However, due to demands for highly accurate simulations, researchers have sought high-order numerical methods over the past few decades. Among various candidates, the discontinuous Galerkin (DG) method has become popular in the high-order commnuity because of its high arithmetic intensity and data locality. Despite the DG method has clear advantages to utilize, some challenges are still remaining for practical usage, especially in transonic flow analysis. In transonic flows, shock waves typically arise due to the acceleration of flows. Consequently, it is critical for a numerical solver to have a shock-capturing capability. In our previous work, we have shown shock-capturing capabilities of the discontinuous Galerkin finite element method (DG-FEM) solver in the open-source SU2 framework by analyzing an inviscid transonic flow over a NACA0012 airfoil in two dimensions. In this paper, we extend the shock-capturing capabilities of the DG-FEM solver to three dimensions by analyzing inviscid transonic flows over the three-dimensional NACA0012 airfoil and the ONERA-M6 wing.